A pressure welding method and to a pressure welding device (1) are provided. The pressure welding device (1) includes a plastification device (7), an upsetting device (8) and component mountings (34, 35, 36, 37) for the components (2, 3, 3′, 4) to be welded together and a machine frame (12). The pressure welding device (1) includes a machine head (13) which is arranged so as to move on the machine frame (12). The machine head (13) includes a rotatable spindle (54) and a component mounting element (34, 35) as well as an associated spindle drive (56). The machine head (13, 14) and the spindle drive (56) are separated from each other on the machine frame (12). A controllable mass decoupling (79) including an axially tolerant coupling (80), is arranged in the drive train (57) between the fixed or moveable spindle drive (56) arranged on the machine frame (12).

A method of manufacturing a mechanical part of the present invention includes a first process of forming, by performing a folding processing to an end portion of the material, a portion to be processed having a structure, in which a plurality of layers respectively having a thickness corresponding to a plate thickness of a material overlap each other, in the material such that a plate thickness direction of the layer is orthogonal to a plate thickness direction of the material; and a second process of changing, by performing a forging processing to the portion to be processed, a shape of the portion to be processed to a target shape while press-welding the layers of the portion to be processed to each other by plastic deformation.

A method of manufacturing a mechanical part of the present invention includes a first process of forming, by performing a folding processing to an end portion of the material, a portion to be processed having a structure, in which a plurality of layers respectively having a thickness corresponding to a plate thickness of a material overlap each other, in the material such that a plate thickness direction of the layer is orthogonal to a plate thickness direction of the material; and a second process of changing, by performing a forging processing to the portion to be processed, a shape of the portion to be processed to a target shape while press-welding the layers of the portion to be processed to each other by plastic deformation.

A laser beam machining method and a laser beam machining device capable of cutting a work without producing a fusing and a cracking out of a predetermined cutting line on the surface of the work, wherein a pulse laser beam is radiated on the predetermined cut line on the surface of the work under the conditions causing a multiple photon absorption and with a condensed point aligned to the inside of the work, and a modified area is formed inside the work along the predetermined determined cut line by moving the condensed point along the predetermined cut line, whereby the work can be cut with a rather small force by cracking the work along the predetermined cut line starting from the modified area and, because the pulse laser beam radiated is not almost absorbed onto the surface of the work, the surface is not fused even if the modified area is formed.

A bonding method is capable of realizing high bonding strength and connection reliability even at a connection part in a high temperature area by means of simple operation low temperature bonding. The method includes a first step wherein, on at least one of the bonded surfaces of two materials to be bonded having a smooth surface, a thin film of noble metal with a volume diffusion coefficient greater than that of the base metal of the material to be bonded is formed using an atomic layer deposition method at a vacuum of 1.0 Pa or higher, a second step wherein a laminate is formed by overlapping the two materials to be bonded so that the bonded surfaces of the two materials are connected through the thin film, and a third step wherein the two materials to be bonded are bonded by holding the laminate at a predetermined temperature.

An apparatus and method for protecting an inner radial surface of a radial member of a turbomachine from corrosion are provided. The method may include shaping the inner radial surface of the radial member and a corresponding outer radial surface of a corrosion-resistant liner. The method may also include heating the radial member to increase a diameter of the inner radial surface of the radial member, and inserting at least a portion of the corrosion-resistant liner into the radial member. The method may further include attaching the corrosion-resistant liner to the inner radial surface of the radial member to thereby protect the inner radial surface of the radial member of the turbomachine from corrosion.

An apparatus and method for protecting an inner radial surface of a radial member of a turbomachine from corrosion are provided. The method may include shaping the inner radial surface of the radial member and a corresponding outer radial surface of a corrosion-resistant liner. The method may also include heating the radial member to increase a diameter of the inner radial surface of the radial member, and inserting at least a portion of the corrosion-resistant liner into the radial member. The method may further include attaching the corrosion-resistant liner to the inner radial surface of the radial member to thereby protect the inner radial surface of the radial member of the turbomachine from corrosion.

Described is a design and method for producing a sputtering target assembly with low deflection made from target material solder bonded to composite backing plate with coefficient of thermal expansion (CTE) matching the target material. The composite backing plate is composite configuration composed of at least two different materials with different CTE. The composite backing plate, after plastic deformation, if necessary, has a CTE matching the target material and low and desirable deflection in the bonding process, and therefore, resulting in a low deflection and low stress target material bonded to composite backing plate assembly. The method includes manufacturing composite backing plate with a flat bond surface, heat treating of target blank and composite backing plate to achieve desirable shape of bond surfaces, solder bonding target to a backing plate, and slowly cooling the assembly to room temperature. Matching CTE in both target material and backing plate eliminates the problem of CTE mismatch and prevents the assembly from deflection and internal stress.

Described is a design and method for producing a sputtering target assembly with low deflection made from target material solder bonded to composite backing plate with coefficient of thermal expansion (CTE) matching the target material. The composite backing plate is composite configuration composed of at least two different materials with different CTE. The composite backing plate, after plastic deformation, if necessary, has a CTE matching the target material and low and desirable deflection in the bonding process, and therefore, resulting in a low deflection and low stress target material bonded to composite backing plate assembly. The method includes manufacturing composite backing plate with a flat bond surface, heat treating of target blank and composite backing plate to achieve desirable shape of bond surfaces, solder bonding target to a backing plate, and slowly cooling the assembly to room temperature. Matching CTE in both target material and backing plate eliminates the problem of CTE mismatch and prevents the assembly from deflection and internal stress.

A method of constructing a plate fin heat exchanger includes joining a first side bar formed from a nickel-iron alloy to a first end of a fin element formed from a nickel-iron alloy through a first nickel-iron alloy bond, and joining a second side bar formed from a nickel-iron alloy to a second end of the fin element through a second nickel-iron alloy bond to create a first layer of the plate fin heat exchanger. The fin element defines a fluid passage.